CN215589004U - Blade baffle plate disassembling tool - Google Patents

Abstract

One object of the present invention is to provide a dismounting tool which can complete dismounting of a blade baffle without damaging the blade. The blade baffle dismounting tool for achieving the purpose comprises a supporting assembly, an adapter and a force application assembly. The support component is arranged on the inner edge of the turbine disc and is provided with a connecting part, and the connecting part is positioned at the center of the turbine disc in the installation state. The adapter is rotatably hinged to the connection part along the axis of the turbine disk. The force application assembly is provided with a connecting end and a force application end, the connecting end is hinged with the adaptor, the hinged force application assembly can rotate relative to the adaptor along a first axis, the first axis is perpendicular to the axis of the turbine disk, the force application end is provided with at least one insertion unit, and when the force application assembly rotates relative to the adaptor, at least one part of the insertion unit can be inserted into at least one groove of the blade baffle.

Description

Blade baffle plate disassembling tool

Technical Field

The utility model relates to the field of engine assembly, in particular to a blade baffle plate disassembling tool.

Background

In the assembly of an aircraft engine, which includes the assembly and disassembly of blade baffles, as shown in fig. 1 to 3, the prior engine turbine rotor is schematically illustrated, and the engine turbine rotor is composed of a disk drum 90 and blades 91, wherein the blades 91 are connected with a mortise in the circumferential direction of the disk drum 90 through dovetail type or fir tree type tenon teeth, and the mortise is matched with the tenon teeth of the blades 91 to limit the freedom of movement (non-rotation) in the circumferential direction of the blades 91. A multistage shutter 92 is provided between the vane 91 and the drum 90, and the shutter 92 is fitted into the catching groove 911 of the vane 91 and the catching groove 901 of the drum 90 to restrict the axial movement of the vane 91.

Wherein, be provided with a plurality of slot parts 920 on the baffle 92, when the assembly, need block the card portion 921 that goes up between a plurality of slot parts 920 on every segmentation baffle 92 and block into the draw-in groove 911 that forms to blade jack catch 912 department, in order to accomplish the assembly of whole circle segmentation baffle 92 in proper order. During disassembly, the baffle 92 (multiple segments) forming the whole ring needs to be rotated at a small angle, so that the groove portions 920 on the baffle 92 are aligned with the blade claws 912 (the baffle is separated from the blade claws), and then the baffle 92 is pushed outwards in the radial direction, so that the baffle 92 is separated from the clamping groove 911 of the turbine disc, and then the baffle 92 is separated from the turbine disc.

However, the inventor found that after the engine is operated, the baffle 92 has a large tightness with the blade jaws 912 and the drum 90 due to thermal stress, and the baffle 92 needs to be driven to rotate by the inertia force generated by striking a screwdriver (or a core rod) with a hammer during the disassembly until the groove portions 920 on the baffle 92 are located at the blade jaws 912. In the actual operation process, often because there is great tightness between baffle and blade jack catch and the turbine dish, strike the unable whole circle baffle of drive of single baffle and take place to rotate, then need strike each baffle one by one this moment for the rotatory small angle of each baffle, through strike the back one by one many rounds repeatedly, just can be with the rotatory to blade jack catch department of slot part on the baffle. Because the blade baffle is the thin slice structure, and thickness is less than 1.2mm, and the slot part of baffle is nearer with the blade, adopts the mode that the hand hammer strikeed screwdriver (or plug) to realize the decomposition of blade baffle or the in-process of assembling, and the screwdriver (or plug) is deviate from in the slot part of baffle easily, hits the blade, causes the blade damage.

SUMMERY OF THE UTILITY MODEL

One object of the present invention is to provide a dismounting tool which can complete dismounting of a blade baffle without damaging the blade.

To achieve the foregoing object, a blade barrier attaching and detaching tool for attaching and detaching a blade barrier between a blade and a turbine disk, the blade barrier having a plurality of catching portions and a plurality of groove portions formed between the catching portions, the attaching and detaching tool includes:

the support assembly is arranged on the inner edge of the turbine disc and is provided with a connecting part, and the connecting part is positioned at the center of the turbine disc in an installation state;

an adaptor to rotatably articulate with the connection portion along the turbine disk axis; and

the force application assembly is provided with a connecting end and a force application end, the connecting end is hinged to the adaptor, the hinged force application assembly can rotate relative to the adaptor along a first axis, the first axis is perpendicular to the axis of the turbine disc, the force application end is provided with at least one insertion unit, and when the force application assembly rotates relative to the adaptor, at least one part of the insertion unit can be inserted into at least one groove of the blade baffle.

In one or more embodiments, the force application assembly comprises:

the force application rod is provided with the connecting end;

the fixing seat is provided with a sleeve ring part and a body part, the fixing seat is sleeved on the force application rod through the sleeve ring part, and the body part is provided with the force application end; and

and the bolt is used for connecting the sleeve ring part and the force application rod.

In one or more embodiments, the force applying end is a protrusion protruding from the body portion to both sides, and the insertion unit is a pair provided corresponding to each protrusion;

when the force application assembly rotates relative to the adaptor, at least one part of any one insertion unit can be inserted into the groove part of the blade baffle plate.

In one or more embodiments, the insertion unit is a bolt provided on the convex portion.

In one or more embodiments, the bottom surface of the fixed seat, which is in contact with the turbine disc, is provided with a boss part, so that an avoiding notch is formed on one side, facing the blade, of the bottom surface of the fixed seat;

when the boss part is in contact with the inner edge of the turbine disc, the avoiding notch avoids the edge plate of the blade.

In one or more embodiments, a position limiting portion is further disposed at a joint of the adaptor and the connecting end, and the position limiting portion limits a rotation range of the force application assembly relative to the adaptor.

In one or more embodiments, the connecting portion is a protruding shaft protruding from the support assembly, an axis of the protruding shaft passes through a hub of the turbine disk in an installation state, and the adaptor has a ring portion, and the ring portion is sleeved outside the protruding shaft so that the adaptor is hinged to the connecting portion.

In one or more embodiments, the support assembly includes a first plate and a second plate, and the first plate and the second plate are respectively clamped to the inner edge of the turbine disk from two sides of the turbine disk in the axial direction and then connected by a fastener.

In one or more embodiments, the first plate has a first spigot portion and a second spigot portion, and the second plate has a third spigot portion and a fourth spigot portion, and in the clamped state, the first spigot portion is in butt joint with the third spigot portion, and the second spigot portion is in butt joint with the fourth spigot portion, so as to form clamping grooves clamped at the inner edge of the turbine disc respectively;

the distance between the bottoms of the two clamping grooves corresponds to the inner diameter of the inner edge of the turbine disc, and the connecting part is positioned in the middle of the two bottoms of the grooves.

In one or more embodiments, the force application assembly is removably hinged to the adaptor via an adaptor pin.

The advanced effects of the utility model include one or a combination of the following:

1) this assembly and disassembly tools passes through the adaptor, has realized that the insert unit inserts fast or breaks away from the slot part of blade baffle, through the articulated department of rotating adaptor and connecting portion afterwards, can be convenient for dismantle so that it is from the assembly position to blade baffle application of force. Simultaneously, because adaptor and connecting portion are 360 rotatable in articulated department, can make this assembly and disassembly tools can promote the blade baffle of optional position and take place small angular rotation, realize the decomposition of blade baffle, reduced because of knocking the blade damage that leads to.

2) Be provided with in this assembly and disassembly tools and dodge groove and spacing portion to reduce the in-process of dismouting blade baffle and to the phenomenon of rubbing of blade, further reduced the damage to the blade.

3) The dismounting tool is simple in structure and easy to assemble and operate.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 shows a schematic view of a blade barrier in an installed state;

FIG. 2 is a schematic view of another angle in the blade barrier installation;

FIG. 3 shows a schematic view of a blade barrier in an uninstalled state;

FIG. 4 is a perspective view of the present assembly/disassembly tool in an assembled/disassembled state;

FIG. 5 shows a half-section schematic of FIG. 4;

FIG. 6 is a perspective view of one embodiment of the present assembly and disassembly tool;

FIG. 7 shows a half-section schematic of FIG. 6;

FIG. 8 illustrates a perspective view of one embodiment of the present force application assembly;

FIG. 9 shows a half-section schematic of FIG. 8;

figure 10 shows a perspective view of one embodiment of the present support assembly.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed.

Also, the present application uses specific words to describe embodiments of the application, such as "one embodiment," "an embodiment," and/or "some embodiments" to mean that a particular feature, structure, or characteristic described in connection with at least one embodiment of the application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate. In addition, the terms "first", "second", and the like are used to define the components, and are used only for convenience of distinguishing the corresponding components, and the terms do not have special meanings unless otherwise stated, and therefore, the scope of the present application is not to be construed as being limited.

It should be noted that, where used, the upper, lower, top, and bottom in the following description are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.

It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the utility model as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.

To solve at least one aspect of the problems in the prior art, the present invention provides a disassembly and assembly tool.

Receiving a blade barrier 92 shown in the background art in fig. 1 to 3, which is fitted between the blade 91 and the turbine disk (disk drum 90) in a fitted state, the blade barrier 92 has a plurality of catching portions 921 and a plurality of groove portions 920 formed between the plurality of catching portions 921.

Fig. 4 is a perspective view showing a state where the attaching and detaching tool is attached and detached according to an embodiment of the attaching and detaching tool, fig. 5 is a half-sectional view of fig. 4, fig. 6 is a perspective view showing a state where the attaching and detaching tool is attached and detached according to an embodiment of the attaching and detaching tool, and fig. 7 is a half-sectional view of fig. 6.

The dismounting tool comprises a support component 1, an adapter 2 and a force application component 3, wherein the support component 1 is arranged on the inner edge 900 of the turbine disk and is provided with a connecting part 10, and in the mounting state shown in the figure, the connecting part 10 is positioned at the center of the turbine disk.

The adaptor 2 is hinged to the connecting portion 10, and the hinged adaptor 2 is rotatable relative to the connecting portion 10 about a turbine disk axis a. It will be appreciated that the turbine disc is a generally annular member, with the turbine disc axis a referring to the central axis of the turbine disc.

The force application assembly 3 is provided with a connecting end 30 and a force application end 31, the connecting end 30 is hinged with the adaptor 2, the hinged force application assembly 3 can rotate relative to the adaptor 2 by taking a first axis b as a rotation center, the first axis b is perpendicular to an axis a of the turbine disk, the force application end 31 is provided with two insertion units 32, and when the force application assembly 3 rotates relative to the adaptor 2 by taking the first axis b as the rotation center, at least one part of the two insertion units 32 can be inserted into the groove part 920 of the blade baffle.

During assembly, the force application component 3 and the adaptor 2 thereof are rotated by taking the axis a of the turbine disk as the center, so that the two insertion units 32 are simultaneously and approximately aligned with the two groove portions 920 of the blade baffle plate to be assembled, then the force application component 3 is rotated by taking the axis b of the turbine disk as the center, and the force application component 3 and the adaptor 2 thereof are simultaneously and continuously adjusted by taking the axis a of the turbine disk as the center, so that the two insertion units 32 are aligned and smoothly inserted into the groove portions 920, and then the force application component 3 and the adaptor 2 thereof are rotated by taking the axis a of the turbine disk as the center, so that a force along the circumferential direction of the turbine disk is applied to the blade baffle plate until the clamping portion 921 of the blade baffle plate is assembled between the blade and the turbine disk. The force applying member 3 is then rotated about the first axis b, so that the insertion unit 32 is removed from the groove portion 920, thereby completing the assembly.

During disassembly, the force application component 3 and the adaptor 2 thereof are rotated around the turbine disk axis a, so that the two insertion units 32 are simultaneously and approximately aligned with the two groove portions 920 of the blade baffle plate to be assembled, then the force application component 3 is rotated around the first axis b, and the force application component 3 and the adaptor 2 thereof are simultaneously rotated around the turbine disk axis a and continuously adjusted so that the two insertion units 32 are aligned and smoothly inserted into the groove portions 920, then the force application component 3 and the adaptor 2 thereof are rotated around the turbine disk axis a, so that a force along the circumferential direction of the turbine disk is applied to the blade baffle plate until the clamping portion 921 of the blade baffle plate can be disengaged from the root portion of the blade, then the force application component 3 is rotated around the first axis b so that the insertion units 32 are disengaged from the groove portions, and then the blade baffle plate 920 is pushed outwards along the radial direction so that the blade baffle plate is disassembled from the turbine disk, thereby completing the disassembly.

It will be understood that in the embodiment shown in the figures, the number of the insertion units 32 at the force application end 31 is two, at least a part of the two insertion units 32 are simultaneously inserted into the groove 920 of the blade barrier during assembly or disassembly, and in other embodiments different from those shown, the number of the insertion units 32 may be other suitable numbers, such as 1, 3 or more. During assembly or disassembly, the or each insertion unit is inserted into the slot portion of the blade flap.

This assembly and disassembly tools passes through adaptor 2, has realized that the cell 32 inserts fast or breaks away from the slot part of blade baffle, through the articulated department of rotating adaptor 2 and connecting portion 10 afterwards, can be convenient for to blade baffle application of force so that it is dismantled from the assembly position. Simultaneously, because adaptor 2 is 360 rotatable with connecting portion 10 in articulated department, can make this assembly and disassembly tools can promote the blade baffle of optional position and take place small angular rotation, realize the decomposition of blade baffle, reduced because of knocking the blade damage that leads to.

Although one embodiment of the present disassembly tool is described above, in other embodiments of the present disassembly tool, the present disassembly tool may have more details than the above-described embodiments in many respects, and at least a portion of the details may have various variations. At least some of these details and variations are described below in several embodiments.

Fig. 8 shows a perspective view of one embodiment of the force application assembly, and fig. 9 shows a half-section view of fig. 8. In one embodiment of the present dismounting tool, the force application assembly 3 includes a force application rod 33, a fixing seat 34 and a latch 35, wherein the force application rod 33 has a connection end 30, the fixing seat 34 includes a collar portion 340 and a body portion 341, the fixing seat 34 is connected to the force application rod 33 by the collar portion 340 in a sleeved manner, and the body portion 34 has a force application end 31. After the fixed seat 34 is connected to the force application rod 33, it is fixed by the latch 35. Specifically, the force application rod 33 has a shoulder 331 and is provided with a connecting hole, the collar portion 340 is also provided with a through hole, when the collar portion 340 is sleeved on the force application rod 33 and abuts against the shoulder 331, the connecting hole is aligned with the through hole, and the bolt 35 is inserted at this time, so that the force application rod 33 is connected with the fixing seat 34. Meanwhile, in the connected state, the insertion unit 32 can move to a position aligned with the groove portion 920 of the blade shutter.

Further, the force applying end 31 is a protrusion protruding from the body 341 of the fixing base 34 to both sides, and the inserting unit 32 is disposed corresponding to each protrusion.

Further, the body 341 has a threaded hole on the protruding portion protruding to both sides, the inserting unit 32 is a bolt disposed in the threaded hole, and by rotating the bolt, the distance that the inserting unit 32 protrudes from the fixing seat 34 can be adjusted, thereby facilitating the adjustment of the distance that the inserting unit 32 is inserted into the groove portion 920 of the blade guard.

It can be understood that, in the embodiment shown in the figures, the force application assembly 3 is formed by connecting the force application rod 33, the fixing seat 34, the latch 35 and the insertion unit 32, which are respectively connected, so that during the use process, a single accessory can be replaced according to the requirement to adapt to different assembly occasions. Of course, in other embodiments, the force application assembly 3 may be a single piece of suitable construction.

In one embodiment of the present dismounting tool, the bottom surface of the fixed base 34 contacting the turbine disk has a boss portion 342, such that a side of the bottom surface of the fixed base 34 facing the blade is formed with an escape notch 343, wherein when the blade barrier is assembled or disassembled, the boss portion 342 contacts with the inner edge of the turbine disk, and at this time, the escape notch 343 can escape from the edge plate of the blade, so as to further reduce the possibility of damage to the blade during dismounting.

Further, in an embodiment of the present dismounting tool, the joint of the adaptor 2 and the connection end 30 of the force application component 3 further has a limiting portion 22, and when the force application component 3 rotates relative to the adaptor 2, the limiting portion 22 can abut against the force application component 3 to limit the rotation range of the force application component relative to the adaptor 2, so as to avoid the blade from being damaged due to over-rotation of the force application component 3, and further reduce the possibility of damage to the blade in the dismounting process.

As shown in fig. 10, which is a perspective view illustrating an embodiment of the present support assembly, in an embodiment of the present dismounting tool, the connection portion 10 is a protruding shaft protruding from the support assembly 1, an axial center of the protruding shaft passes through a disk center of the turbine disk in an installation state as shown in the drawing, the adaptor 2 has a ring portion 23, and the adaptor 2 is hinged to the connection member 10 by sleeving the ring portion 23 on an outer side of the connection portion 10 in a protruding shaft shape. In one embodiment, the ring portion 23 is sleeved outside the connecting portion 10 and then limited by the limiting ring 13, so as to prevent the ring portion 23 from coming off the connecting portion 10.

In other embodiments, which are different from those shown in the figures, the adaptor may have a shaft portion and the connecting portion may be a ring portion.

In one embodiment of the present disassembly and assembly tool, the support assembly 1 includes a first plate 14 and a second plate 15, and the first plate 14 and the second plate 15 are respectively clamped by the inner rim 900 of the turbine disk from both sides of the turbine disk in the axial direction a and then connected by a fastener. In other embodiments, the support assembly may be in the form of other support members, such as a support frame or a support base.

In one embodiment of the present dismounting tool, the first plate 14 has a first and a second stop portion 141, 142, and the second plate 15 has a third and a fourth stop portion 151, 152, wherein, in the clamped state as shown in the figure, the first and the second stop portions 141, 142 and 152 are butted to form clamping grooves clamped at the inner rim 90 of the turbine disk, respectively, wherein the distance between the two clamping groove bottom 140 is set corresponding to the inner diameter of the inner rim 90 of the turbine disk, i.e. the distance between the two clamping groove bottom 140 is equal to or slightly larger than the inner diameter of the inner rim 90 of the turbine disk, and the connecting portion 10 is located at the middle position between the two clamping groove bottom 140, so that when the first and the second plate 14, 15 can be assembled at the inner rim 90 of the turbine disk, the connecting portion 10 is located at the disk center of the turbine disk. In other embodiments, the connection portion 10 may be adjusted to the hub position of the turbine disk by multiple times of adjustment.

In one embodiment of the present tool for removing and assembling, the force application member 3 is detachably hinged to the adaptor 2 by an adaptor pin 36 for easy removal, and the first axis b is the central axis of the adaptor pin 36.

Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the utility model, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims (10)

1. A blade barrier attaching and detaching tool for attaching and detaching a blade barrier between a blade and a turbine disk, the blade barrier having a plurality of engaging portions and a plurality of groove portions formed between the engaging portions, the attaching and detaching tool comprising:

the support assembly is arranged on the inner edge of the turbine disc and is provided with a connecting part, and the connecting part is positioned at the center of the turbine disc in an installation state;

an adaptor to rotatably articulate with the connection portion along the turbine disk axis; and

the force application assembly is provided with a connecting end and a force application end, the connecting end is hinged to the adaptor, the hinged force application assembly can rotate relative to the adaptor along a first axis, the first axis is perpendicular to the axis of the turbine disc, the force application end is provided with at least one insertion unit, and when the force application assembly rotates relative to the adaptor, at least one part of the insertion unit can be inserted into at least one groove of the blade baffle.

2. The assembly and disassembly tool of claim 1, wherein the force application assembly comprises:

the force application rod is provided with the connecting end;

the fixing seat is provided with a sleeve ring part and a body part, the fixing seat is sleeved on the force application rod through the sleeve ring part, and the body part is provided with the force application end; and

and the bolt is used for connecting the sleeve ring part and the force application rod.

3. The disassembly and assembly tool of claim 2, wherein the force applying end is a pair of protrusions protruding from both sides of the body portion, and the insertion unit is a pair corresponding to each of the protrusions;

when the force application assembly rotates relative to the adaptor, at least one part of any one insertion unit can be inserted into the groove part of the blade baffle plate.

4. The disassembly and assembly tool of claim 3, wherein the insertion unit is a bolt provided on the convex portion.

5. The assembly and disassembly tool of claim 2, wherein the bottom surface of the fixed seat contacting the turbine disc has a boss portion, so that an escape notch is formed on one side of the bottom surface of the fixed seat facing the blade;

when the boss part is in contact with the inner edge of the turbine disc, the avoiding notch avoids the edge plate of the blade.

6. The assembly and disassembly tool of claim 1 wherein the interface between the adaptor and the connection end further comprises a limiting portion, wherein the limiting portion limits the range of rotation of the force application assembly relative to the adaptor.

7. The disassembly and assembly tool of claim 1, wherein the connecting portion is a protruding shaft protruding from the supporting component, the axis of the protruding shaft passes through the center of the turbine disk in the assembled state, and the adaptor has a ring portion, and the adaptor is hinged to the connecting portion by sleeving the ring portion on the outer side of the protruding shaft.

8. The disassembly and assembly tool of claim 1, wherein the support assembly comprises a first plate and a second plate, and the first plate and the second plate are respectively clamped at the inner edge of the turbine disk from two sides of the turbine disk in the axial direction and then connected by a fastener.

9. The disassembly and assembly tool of claim 8, wherein the first plate has a first spigot portion and a second spigot portion, and the second plate has a third spigot portion and a fourth spigot portion, and in the clamped state, the first spigot portion is abutted with the third spigot portion, and the second spigot portion is abutted with the fourth spigot portion, so as to form clamping grooves clamped at the inner edge of the turbine disc respectively;

the distance between the bottoms of the two clamping grooves corresponds to the inner diameter of the inner edge of the turbine disc, and the connecting part is positioned in the middle of the two bottoms of the grooves.

10. The assembly and disassembly tool of claim 1 wherein the force application assembly is removably hinged to the adaptor via an adaptor pin.

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